Abstract: Platform for an aircraft turbo machine fan rotor, the platform being configured to be secured to a fan disc between two adjacent fan blades. The platform further including a longitudinal wall defining an aerodynamic external face. The wall includes a honeycomb structure interposed between two skins which are respectively an internal skin and an external skin, with the external skin defining the aerodynamic external face.

Abstract: Platform for an aircraft turbo machine fan rotor, the platform being configured to be secured to a fan disc between two adjacent fan blades. The platform further including a longitudinal wall defining an aerodynamic external face. The wall includes a honeycomb structure interposed between two skins which are respectively an internal skin and an external skin, with the external skin defining the aerodynamic external face.

Abstract: A vaned wheel device traversed by a radial drive shaft includes radial arms, one of which contains the shaft, and stationary vanes manufactured separately from the casing and a ferrule and assembled thereto. A sleeve encompassing the shaft traverses the casing and serves to support a bearing for supporting the shaft with positional accuracy, and maintaining tightness by forming a single cavity with the radial arm cavities traversing the shaft.

Abstract: A vaned wheel device traversed by a radial drive shaft includes radial arms, one of which contains the shaft, and stationary vanes manufactured separately from the casing and a ferrule and assembled thereto. A sleeve encompassing the shaft traverses the casing and serves to support a bearing for supporting the shaft with positional accuracy, and maintaining tightness by forming a single cavity with the radial arm cavities traversing the shaft.

Abstract: A structural frame for a turbomachine, such as an intermediate frame or an exhaust frame, the frame including at least two coaxial rings, an inner ring and an outer ring, together with radial arms interconnecting the rings. At least one of these elements includes a plurality of parts that are fastened together by bolting.

Abstract: An extension of an intermediate casing for an aircraft jet engine, intended to project towards the downstream end from an external shell of said intermediate casing is disclosed. This extension includes an annular connecting downstream end forming an annular groove open radially towards the outside, intended to receive nacelle covers. The annular connecting downstream end is produced by a plurality of angular sectors.

Abstract: The invention relates to an intermediate casing (21) for an aircraft jet engine, comprising an outer shell (23) and also front and rear flanges (25, 27) which are arranged radially inside with respect to the outer shell, the casing (21) also comprising structural arms (17) which extend radially between the flanges as far as the shell (23), the rear flange being equipped with receiving means (34) for receiving a fixing bracket for fixing a rod for absorbing the thrust forces, and the first receiving means comprising bosses (36) coming from the rear flange, through which bosses through-orifices (38) are formed which are passed through by fixing screws of the bracket. According to the invention, at least one of the bosses (36) extends as far as making contact with one of the structural arms (17).

Abstract: The present invention relates to an intermediate casing of a turbojet comprising, between an inner hub and an outer cylindrical shroud, a plurality of radial arms at least one of which is hollow, a radial transmission shaft for driving the auxiliary machines being mounted rotatably in said radial arm, a first end of the transmission shaft passing through the inner hub and the second end passing through the outer cylindrical shroud. The housing is notable in that the inner volume consists of a single compartment housing the transmission shaft and forming a passageway for a lubrication fluid.

Abstract: A structural frame for a turbomachine, such as an intermediate frame or an exhaust frame, the frame including at least two coaxial rings, an inner ring and an outer ring, together with radial arms interconnecting the rings. At least one of these elements includes a plurality of parts that are fastened together by bolting.

Abstract: The invention relates to an intermediate casing (21) for an aircraft jet engine, comprising an outer shell (23) and also front and rear flanges (25, 27) which are arranged radially inside with respect to the outer shell, the casing (21) also comprising structural arms (17) which extend radially between the flanges as far as the shell (23), the rear flange being equipped with receiving means (34) for receiving a fixing bracket for fixing a rod for absorbing the thrust forces, and the first receiving means comprising bosses (36) coming from the rear flange, through which bosses through-orifices (38) are formed which are passed through by fixing screws of the bracket. According to the invention, at least one of the bosses (36) extends as far as making contact with one of the structural arms (17).

Abstract: The invention relates to an extension (30) of an intermediate casing for an aircraft jet engine, intended to project towards the downstream end from an external shell of the intermediate casing, this extension comprising an annular connecting downstream end (64) forming an annular groove (66) open radially towards the outside, intended to receive nacelle covers. According to the invention, the annular connecting downstream end (64) is produced by means of a plurality of angular sectors (76a, 76b).

Abstract: The present invention relates to an intermediate casing of a turbojet comprising, between an inner hub and an outer cylindrical shroud, a plurality of radial arms at least one of which is hollow, a radial transmission shaft for driving the auxiliary machines being mounted rotatably in said radial arm, a first end of the transmission shaft passing through the inner hub and the second end passing through the outer cylindrical shroud. The housing is notable in that the inner volume consists of a single compartment housing the transmission shaft and forming a passageway for a lubrication fluid.